Annular combustion chamber in a turbine engine

Abstract

The invention relates to a device for supporting and centring a fuel injector in a turbine engine combustion chamber, which includes means for centring a fuel injector along an axis, which are movable in a plane that is radial to the centring axis ( 52 ) in supporting means intended for being attached to the bottom of an annular chamber ( 18 ). According to the invention, the centring means include at least two radially external tabs ( 54, 56 ) each inserted respectively in a circumferential recess ( 60, 64 ) of the supporting means, the device including circumferential abutment means ( 78, 80, 74, 76, 82, 86, 84, 88 ) of the radial tabs ( 54, 56 ) of the centring means in the circumferential recesses ( 60, 64 ), the circumferential abutment means being configured such as to enable a greater angular displacement of a first ( 54, 154 ) one of the radial tabs in a first circumferential recess ( 60 ) relative to a second ( 56, 156 ) one of the radial tabs in a second circumferential recess ( 64 ).

The invention claimed is: 
     
       1. A device for supporting and centering a fuel injector in a turbine engine combustion chamber, comprising:
 means for centering a fuel injector along a centering axis, wherein the means for centering is movable in a plane that is radial to the centering axis, and 
 supporting means intended for being attached to a bottom of an annular chamber, 
 wherein the means of centering includes at least two radially external tabs, each inserted respectively in a circumferential recess of the supporting means, 
 wherein each of the at least two radially external tabs is associated with a corresponding circumferential abutment means, and 
 wherein the circumferential abutment means are configured to enable a greater angular displacement of a first one of the radially external tabs in a first circumferential recess relative to a second one of the radially external tabs in a second circumferential recess. 
 
     
     
       2. The device according to  claim 1 , wherein the supporting means include an annular edge extending along the centering axis, in which the first and second circumferential recesses accommodating the first and second radially external tabs are arranged. 
     
     
       3. The device according to  claim 2 , wherein the first and second circumferential recesses of the annular edge each open out respectively at an end in a first and a second axial recess extending along the centering axis and opening out at an end of the annular edge. 
     
     
       4. The device according to  claim 3 , wherein the first and second axial recesses and the first and second circumferential recesses form axial and circumferential openings, respectively, of the annular edge through which the first and second radially external tabs radially pass and delimit a respective first and second circumferential tongue of the annular edge. 
     
     
       5. The device according to  claim 4 , wherein the circumferential abutment means of each of the first and second radially external tabs in a second direction of rotation contrary to the first direction of rotation are formed by a free end portion of each of the first and second tongue, which is bent radially outwards in order to serve as a circumferential abutment to the bent free end of the first and second radial tab. 
     
     
       6. The device according to  claim 1 , wherein the circumferential abutment means in a first direction of rotation of each of the first and second radially external tabs around the centering axis are advantageously formed by a respective axial and radial face delimiting a circumferential end of first and second circumferential openings. 
     
     
       7. The device according to  claim 6 , wherein the circumferential abutment means of each of the first and second radially external tabs in a second direction of rotation contrary to the first direction of rotation are formed by an axial and radial face of a first and a second tooth in axial protrusion in the first and second circumferential openings, respectively, wherein each face of the first and second teeth are oriented circumferentially in the opposite direction to said first opening. 
     
     
       8. The device according to  claim 7 , wherein an axial dimension of the circumferential opening measured at the axial and radial wall of the first and second teeth is less than an axial dimension of the radially external tab. 
     
     
       9. The device according to  claim 1 , comprising solely a first and a second radially external tab inserted diametrically opposed to one another and respectively inserted in a first and a second circumferential recess of the supporting means. 
     
     
       10. The device according to  claim 1 , wherein the means of centering include first means of bayonet fixing interacting with second means of bayonet fixing mounted on the supporting means for axial securing of the means of centering on the supporting means. 
     
     
       11. An annular combustion chamber in a turbine engine, comprising at least one device according to  claim 1 . 
     
     
       12. A turbine engine comprising the combustion chamber according to  claim 11 .